Aeroplane



1,462,410 L. JACOBY AEROPLANE {giled Oct. 27. 1922 2 Sheets-Sheet 1 A TTHNEYS 244i AERONAUTlCS July'l'i, 1923.

L. JACOBY AEROPLANE Filed Oct. 27. 1922 2 She'ets-Sheet 2 W/T/VESSES A TTRNEYS 4. 'AtHONAUllUS Patented July 17, 1923.

NITED STATES LYLE JACOBY, 0F PARIS, KENTUCKY.

AEROPLANE.

Application filed October 27, 1922.

To all whom t may concern:

Be it known that I, LYLE JAooY, a citi` zen of the United States, and a resident of Paris, in the county of Bourbon and State of Kentucky, have invented certain new and useful Improvements in Aeroplanes, of which the following is a specification.

This invention relates to aeroplanes.

The invention more particularly relates to improvements in controlling means for aeroplanes and has for its general object to provide controlling means which may be embodied in the structure of an aeroplane and which will permit an exceedingly flexible control of said aeroplane.

It is also an object of the invention that means be provided whereby the normal descent or ascent of an aeroplane may be aocelerated.

It is a further object of the invention that a novel form of stabilizing means be provided for aeroplanes whereby to facilitate the control of the same when in flight It is a still further object of the invention that a novel adjustable means be provided for illuminating the space at the rear or forward to an aeroplane and also beneath the aeroplane.

Other objects, and objects relating to details of construction, combination and arrangement of parts will hereinafter appear in the detailed description to follow.

The invention is illustrated by way of example in the accompanying drawings, 1n which Figure 1 is a view in side elevation of an aeroplane constructed in accordance with the present invention.

Figures 2 and 3 are detailed views illustrating the manner of adjustably supporting the control planes employed in connection with the present invention.

Figures 4 and 5 are detailed views in side elevation illustrating the manner of manipulating the adjustable control planes whereby to decrease and increase, respectively, the speed of flight of the aeroplane.

Figure 6 is a detailed view illustrating the operating means for the stabilizing planes employed.

Referring to the drawings in detail and particularly to Figure 1, A indicates generally a supporting plane which is supported by a suitable running gear comprising the front wheels W and the rear wheels W. Upon the plane A and centrally rela- Serial No. 597,414.

tive to its length there is suitably mounted a fuselage generally indicated by the reference character F, said fuselage being provided with the usual cock-pit generally indicated at C and carrying at its forward end a propeller P which is mounted in the usual manner and driven from an engine housed within the fuselage. At the rear end of the fuselage there is extended u wardly a shaft 10 which is braced by tle member 11 and which carries at its outer end a propeller P2. Also from the rear end of the fuselage there extends a supporting bar or shaft 12 which has pivotally connected thereto as at 13 a tail plane generally indicated by the reference character T. This tail plane comprises the horizontal section 14 and the vertical section 15 and is adapted to be employed for directing the aeroplane upwardly or downwardly. A pair of control cables 16 may be properly connected to the plane T and extended within the fuselage F to a point within convenient reach of the operator. The pivotal connection 13 is adapted to permit the tail plane T to be swung upwardly or downwardly and means are associated with the cables 16 whereby to adjust-ably hold the plane in its adjusted position.

Upon the supporting plane A there is mounted a plurality of uprights or posts 17, preferably four in number, one occurring at each corner of the plane. These posts may be in the form shown and for the purpose of supporting the adjustable planes B. The planes B are preferably three in number as shown, and for connecting the planes to the posts 17 there is provided for each post three sleeves 18, one for each of the planes, said sleeves being slidable upon the post 17, and each sleeve having extending therefrom an arm 19. Each sleeve 18 carries a socket 20, said socket extending laterally therefrom and preferably consisting in a pair of hemispherical members secured to each other by the means of bolts or the like.l as shown to advantage in Figure 2. This socket 2O is adapted to receive a ball 21 formed upon the end of a. pin 22 which extends from the associated plane B. The pins 22 connected with the forward posts or uprights 17 should extend through a slot as at 23 formed in the downwardly turned edges of the planes, and said slot being adapted to permit relative movement of the pin 22. The purpose of this construction will later appear.

Transversely of the fuselage F there is suitably journaled a shaft 24 which has secured at each end a crank arm 25. Each crank arm 25 is connected to the arm 19 of each of the sleeves 18 carried by the associated rear upright 17 through the rods 2,6, said rods being of different length as required and pivotally connected at their lower ends to the outer end of the rod 25 as at 27 and similarly connected, in each instance, to the outer end of the associated arm 19 as at 28. The shaft 24 is also provided with a crank arm 29 which is connected through a link 30 with the lower end of a hand lever 31,

.said lever being fulcrumed as at 32 and being provided with suitable means whereby the same may be held in adjusted position. As is obvious from this construction and as shown in Figure 4 of the drawings, the distance between the rear ends of the planes B may be adjusted. It should also be noted that the movable pins 22 associated with the forward ends of the planes B freely per* mit this movement to the rear ends of the plane.

A second shaft 33 is journaled transversely of the fuselage F and adjacent the forward end thereof, said shaft likewise having secured to each end a crank arm 37 The outer end of each crank arm 37 is connected to the similar end of the arm 19 of each of the sleeves 18 upon the associated forward post 17 through the means of a rod 38. rlhe rods 38 are similar to the rods 26 and each rod has its one end pivotally connected as at 39 to the outer end of the associated crank arm 37 and its one end pivotally connected as at 39 to the outer end of the associated arm 19. The crank 33 also carries an arm 40 extending radially therefrom and which is connected through a link 41 to a second hand lever 42, said hand lever being fulcrumed similarly to the lever 31 at a point intermediate its length and having the link 41 pivotally connected to its lower end. The lever 42 is adapted to be adjustably moved whereby to adjust the distance between the forward ends of the different planes B.

It may be here mentioned that in the different views of the drawings, namely: Figures 1, 4 and 5 but two posts 17 are shown, said posts being a front post and a rear post occurring upon one side of the aeroplane structure. The remaining two posts have not been shown, but it is believed from the description heretofore given, that the arrangement of these posts and the manner in which the same are connected to the planes B may be clearly understood and that further illustration is unnecessary.

Upon one of the forward posts there may be mounted a headlight 42 and a similar headlight 43 may be mounted upon a rear post 17. These headlights are pivotally supported as at 44 so that the same may be rocked in a vertical plane and thereby adjusting the direction o-f the shaft of light emanating from each of the headlights. A hand lever 45 is provided for each of the headlights 42 and 43, and each lever is connected through a cable or cord 46 with its associated headlight whereby the headlights may be adjusted.

Also there is properly mounted inthe fuselage a winding drum as at 50 which is provided with a crank 51 by which the same may be rotated and which is also provided with a pawl and ratchet arrangement as at 52 by which the same may be adjustably held against rotation. To this drum there may be attached the one end of a cable 53, said cable carrying upon its lower end a lamp 54 and a reflector 55. By raising and lowering the lamp 54 the space beneath the aeroplane may be illuminated.

Upon each end portion of the supporting plane A which extends beyond the fuselage F there is mounted a wing generally indicated by the reference character 56. The particular form of the wing 56 is shown in Figure 6, and as illustrated this wing is pivotally supported or secured to the associated plane A as at 57 and a suitable ball and socket connection 58 is provided whereby a rod 59 may be attached to the pivoted end of each of the wings for operating the same. The rods 59 may be extended within convenient reach of the operator of the aeroplane.

It also should be here noted that each of the planes B are slightly curved or bent as at 60 which is for the purpose of increasing the effective operation of these planes when utilized in connection with controlling the flight of the aeroplane. The specific manner in which this particular structure of the plane enters in the operation of the aeroplane will be apparent from the description of the operation of the aeroplane to follow.

ln the use of the present invention, when it is desired to cause the aeroplane to ascend preparatory to a flight, .the planes B may be brought to the position illustrated in Figure 1 and the propellers P3 operated. This will cause an immediate rising of the aeroplane. After the aeroplane has been brought to the desired height the propeller P may be brought into operation for causing horizontal movement of the aeroplane. In case that it is desired to retard the movement of the aeroplane the rear ends of the planes B may be brought together as illustrated in Figure 4, and in case it is desired to increase the speed of the aeroplane then the planes are brought into the position illustrated in Fig. 5. Also in case that it is desired to permit the plane to glide downwardly after the same has been moved to a considerable height then the planes maybe brought to a position as illustrated in Figure 4 to retard the downward movement of the aeroplane; and if exceedingly fast movement of the aeroplane is desired, then the planes B should be brought to the position illustrated in Figure 5. rI`he adjustments of the planes B may be had through the operation of the hand levers 31 and 42 in the manner heretofore described. Also the tail plane T may be manipulated in order to direct the horizontal flight of the aeroplane. The particular manner in which this aeroplane may be operated is entirely obvious and apparent by those skilled in the art and further recitation relative thereto need not be here stated.

In case that it is desired to greatly increase the downward movement of the aeroplane then the propeller P2 may be brought into operation and in this way the descent of the aeroplane may be exceedingly rapid. Should the aeroplane tend to tilt to one side, then the wings 56 may be brought into operation in order to stabilize the plane, that is, when it is desired to prevent tilting in a certain direction, the plane 56 upon the lower side of the aeroplane is swung outwardly and serves as a stabilizing plane.

It is thought to be entirely apparent the manner in which the lights 42 may be operated to illuminate the space either before or at the rear of the aeroplane. It is also thought entirely clear the manner in which the light 54 may be utilized to illuminate the space beneath the aeroplane.

I claim 1. An aeroplane construction comprising a supporting plane, a plurality of uprights carried thereby, said uprights being preferably four in number and two arranged at the rear end of the supporting plane and two at the forward end thereof, a plurality of collars carried by each of said uprights and freely slidable thereon, a plurality of planes superposed with relation to each other and arranged longitudinally of said aeroplane, said planes being disposed between the pair of posts occurring at the rear end of the aeroplane and also between the pair of posts occurring at the forward end of the aeroplane, connecting means between the collars and planes adapted to permit the similar ends of the planes to be adjusted with respect to each other and combined push rod and lever means operable from the aeroplane whereby the planes may be adjusted.

2. An aeroplane construction comprising a supporting plane, a plurality of uprights carried thereby, said uprights being preferably four in number and two arranged at the rear end of the supporting plane and two at the forward end thereof, a plurality of collars carried by each of said uprights and freely slidable thereon, a plurality of planes superposed with relation to each other and arranged longitudinally of said aeroplane, said planes being disposed between the pair of posts occurring at the rear end of the aeroplane and also between the pair of posts occurring at the forward end of the aeroplane, and means pivotally and slidably connecting said collars and planes, whereby to permit the similar ends of the planes to be adjusted with respect to each other.

3. An aeroplane construction comprising a supporting plane, a plurality of uprights carried thereby, said uprights being preferably four in number and two arranged at the rea-r end of the supporting plane and two at the forward end thereof, a plurality of collars carried by each of said uprights and freely slidable thereon, a plurality of planes superposed with relation to each other and arranged longitudinally of said aeroplane, said planes being disposed between the pair of posts occurring at the rear end of the aeroplane and also between the pair of posts occurring at the forward end of the aeroplane, and connecting means between the collars and planes adapted to permit the similar ends of the planes to be adjusted with respect to each other.

LYLE JACOBY. 

